CN107687780B - Heat exchanger plates with streamlined rib structure and the printed circuit sheet heat exchanger comprising it - Google Patents
Heat exchanger plates with streamlined rib structure and the printed circuit sheet heat exchanger comprising it Download PDFInfo
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- CN107687780B CN107687780B CN201710663123.7A CN201710663123A CN107687780B CN 107687780 B CN107687780 B CN 107687780B CN 201710663123 A CN201710663123 A CN 201710663123A CN 107687780 B CN107687780 B CN 107687780B
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- heat exchanger
- section
- camber line
- circle
- aerofoil profile
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F28—HEAT EXCHANGE IN GENERAL
- F28D—HEAT-EXCHANGE APPARATUS, NOT PROVIDED FOR IN ANOTHER SUBCLASS, IN WHICH THE HEAT-EXCHANGE MEDIA DO NOT COME INTO DIRECT CONTACT
- F28D9/00—Heat-exchange apparatus having stationary plate-like or laminated conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall
- F28D9/0031—Heat-exchange apparatus having stationary plate-like or laminated conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall the conduits for one heat-exchange medium being formed by paired plates touching each other
- F28D9/0037—Heat-exchange apparatus having stationary plate-like or laminated conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall the conduits for one heat-exchange medium being formed by paired plates touching each other the conduits for the other heat-exchange medium also being formed by paired plates touching each other
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F28—HEAT EXCHANGE IN GENERAL
- F28F—DETAILS OF HEAT-EXCHANGE AND HEAT-TRANSFER APPARATUS, OF GENERAL APPLICATION
- F28F3/00—Plate-like or laminated elements; Assemblies of plate-like or laminated elements
- F28F3/02—Elements or assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with recesses, with corrugations
- F28F3/04—Elements or assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with recesses, with corrugations the means being integral with the element
- F28F3/048—Elements or assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with recesses, with corrugations the means being integral with the element in the form of ribs integral with the element or local variations in thickness of the element, e.g. grooves, microchannels
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F28—HEAT EXCHANGE IN GENERAL
- F28F—DETAILS OF HEAT-EXCHANGE AND HEAT-TRANSFER APPARATUS, OF GENERAL APPLICATION
- F28F3/00—Plate-like or laminated elements; Assemblies of plate-like or laminated elements
- F28F3/08—Elements constructed for building-up into stacks, e.g. capable of being taken apart for cleaning
- F28F3/10—Arrangements for sealing the margins
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F28—HEAT EXCHANGE IN GENERAL
- F28F—DETAILS OF HEAT-EXCHANGE AND HEAT-TRANSFER APPARATUS, OF GENERAL APPLICATION
- F28F2250/00—Arrangements for modifying the flow of the heat exchange media, e.g. flow guiding means; Particular flow patterns
- F28F2250/02—Streamline-shaped elements
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- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Heat-Exchange Devices With Radiators And Conduit Assemblies (AREA)
Abstract
The present invention provides a kind of heat exchanger plates with streamlined rib structure and include its printed circuit sheet heat exchanger, streamlined rib it is upper, first section of lower camber line extends to from maximum inscribed circle position from wing leading edge, first section is spirogyrate smooth curve, the rear end of spirogyrate smooth curve and maximum inscribed circle are tangent, second section is extended to from maximum inscribed circle from wing rear, second section is concave shaped smooth curve, and the front end of concave shaped smooth curve and maximum inscribed circle are tangent, first section and the second section form smooth full curve at maximum inscribed circle.The present invention passes through the redesign and optimization to aerofoil profile rib self structure, so that heat exchanging fluid is when flowing through each aerofoil profile rib, change before and after aerofoil profile rib maximum width more acutely, to improve the heat exchange property of airfoil passage, it is designed by the structure to aerofoil profile leading edge and rear, so as to more preferably heat exchanging fluid be guided to flow, the droop loss of airfoil passage is then reduced.
Description
Technical field
The present invention relates to field of heat exchangers more particularly to a kind of heat exchanger plates with streamlined rib structure and include the heat exchange
The printed circuit board heat exchanger of plate.
Background technique
Printed circuit board heat exchanger is a kind of high temperature high voltage resistant, high-efficiency compact formula heat exchanger, is led in heat exchange board channel
Overetch or mach mode process minute fluid channel, finally combine heat exchange plate one by Diffusion Welding mode
It rises, forms heat exchange core body.At present in printed circuit board heat exchanger, common heat exchanger plates channel design form include straight channel,
Wavy channel etc., relative to straight channel, wavy channel heat exchange property is improved but pressure drop is also significantly increased.In order to improve heat exchanger channels
Pressure drop, many new structures are devised, such as airfoil passage shown in FIG. 1 etc..As shown in Fig. 2, existing aerofoil profile is logical
In road, aerofoil profile rib structure generallys use conventional symmetrical airfoil, such as NACA series aerospace aerofoil profile, passes through the length to aerofoil profile rib
Lc, width Lt, the optimization of the channels key design parameters such as front and back pitch Ls, left and right pitch Lv between adjacent aerofoil rib can be with
Improve heat exchange property and the pressure drop of heat exchanger channels.But airfoil passage conventional at present still has heat exchange property and droop loss
Not the problem of not being able to satisfy actual demand.
Summary of the invention
For shortcoming and defect of the existing technology, the present invention is intended to provide a kind of streamlined rib structure heat exchanger plates and packet
Printed circuit sheet heat exchanger containing the heat exchanger plates, by the redesign and optimization to aerofoil profile rib self structure, so that heat exchange stream
Body changes before and after aerofoil profile rib maximum width when flowing through each aerofoil profile rib more acutely, to improve the heat-exchange performance of airfoil passage
Can, it is designed by the structure to aerofoil profile leading edge and rear, so as to more preferably heat exchanging fluid be guided to flow, then reduces aerofoil profile
The droop loss in channel.
The present invention is that technical solution used by solving its technical problem is:
A kind of heat exchanger plates with streamlined rib structure, including substrate and setting are in column-row arrangement in the substrate surface
Multiple streamlined ribs, the cross section of the streamlined rib is substantially in symmetrical airfoil structure, including leading edge, rear, upper camber line and
Lower camber line, the line between aerofoil profile leading edge and rear be formed as the wing middle camber line, the upper camber line and lower camber line about
The middle camber line is symmetrical above and below, and the maximum gauge of the aerofoil profile is formed at the maximum inscribed circle position of the upper and lower camber line, institute
The center location for stating maximum inscribed circle is located on the middle camber line, which is characterized in that
The upper and lower camber line includes the first section and the second section, wherein
First section extends to from maximum inscribed circle position from the wing leading edge, and first section is evagination
Shape smooth curve, the rear end of the spirogyrate smooth curve and the maximum inscribed circle are tangent,
Second section is extended to from the maximum inscribed circle from wing rear, and second section is concave shaped light
Sliding curve, and the front end of the concave shaped smooth curve and the maximum inscribed circle are tangent,
And
First section and the second section form smooth full curve at the maximum inscribed circle.
Preferably, the diameter of the maximum inscribed circle is the 15%~30% of the middle arc length.
Preferably, the aerofoil profile is formed as smooth front end in its edge.Further, the spirogyrate smooth curve
Front end is tangent with nose radius.
Further, the distance between the center of circle of the maximum inscribed circle and leading edge be the middle arc length 25%~
35%, and the rear end of the concave shaped smooth curve at the rear with the middle tangential, the aerofoil profile is at rear
Be formed as wedge angle.Further, the concave shaped smooth curve is the circle arc curve of indent, the center of circle of the circle arc curve
Line with rear point is perpendicular to the middle camber line.
Further, the distance between the center of circle of the maximum inscribed circle and leading edge be the middle arc length 50% with
On, the aerofoil profile is formed to have the smooth fillet of certain radian at edge behind, the rear end of the concave shaped smooth curve with
The rear fillet is tangent.Further, the spirogyrate smooth curve be evagination circle arc curve, the center of circle and it is described most
The line of big incenter is perpendicular to the middle camber line；The concave shaped smooth curve is the circle arc curve of indent, described
The center of circle of circle arc curve and the line of rear point are perpendicular to the middle camber line.
Preferably, the streamlined rib is formed in the substrate using chemical etching, laser-induced thermal etching or mach mode
On.
Preferably, the substrate be thickness be not less than 0.2mm metal plate, it is preferable that the metal plate be 316,304,
The metal sheet of the materials such as 316L, TA1, TC4.
According to another aspect of the present invention, a kind of printed circuit sheet heat exchanger is additionally provided, it is of the invention including several
The above-mentioned heat exchanger plates with streamlined rib structure, wherein the heat exchanger plates with streamlined rib structure mutually stack, and pass through
The mode of Diffusion Welding is formed as whole.
Printed circuit sheet heat exchanger of the invention, the metal substrate for processing streamlined rib structure is stacked, is passed through
Diffusion Welding mode is finally combined into entirety, and last both ends increase end socket and form complete PCHE heat exchanger.After being successful, rib
Upper surface is connected together with the lower end surface of top panel by Diffusion Welding, to make gap section structure between one piece of heat exchange rib of slab
At runner.A laminate be can be by hot fluid, a laminate, can also be another with plurality of plates by a kind of fluid by cold fluid
A little plates are by one other fluid, to achieve the purpose that heat exchange.
Compared with the existing technology, it heat exchanger plates provided by the invention with streamlined rib structure and is changed comprising printed circuit board
Hot device, by the redesign and optimization to aerofoil profile rib self structure, so that heat exchanging fluid is when flowing through each aerofoil profile rib, in aerofoil profile
Variation is more violent before and after rib maximum width, to improve the heat exchange property of airfoil passage, by aerofoil profile leading edge and rear
Structure design, so as to more preferably heat exchanging fluid be guided to flow, then reduces the droop loss of airfoil passage.
Detailed description of the invention
Fig. 1 is airfoil passage structure heat exchanger plates structural schematic diagram.
Fig. 2 is the cross-sectional view of airfoil passage structure.
Fig. 3 is airfoil structure schematic diagram, wherein (A) is existing airfoil structure schematic diagram, and (B) is of the invention be suitable for
The airfoil structure schematic diagram of small flow, (C) are the airfoil structure schematic diagram suitable for big flow of the invention.
Fig. 4 is airfoil structure positioning method schematic diagram, wherein (A) is existing airfoil structure schematic diagram, and (B) is the present invention
The airfoil structure schematic diagram suitable for small flow, (C) be the airfoil structure schematic diagram suitable for big flow of the invention.
Fig. 5 is to be conducted heat and flowed numerical simulation schematic diagram under length and width the same terms in three kinds of rib structures,
Wherein, (A) is heat transfer factor schematic diagram, and (B) is Pressure drop factor schematic diagram.
Fig. 6 is the channel design comprehensive comparison schematic diagram of three kinds of rib structures.
Specific embodiment
To make the objectives, technical solutions, and advantages of the present invention more comprehensible, right hereinafter, referring to the drawings and the embodiments,
The present invention is further described.
As shown in Figure 3,4, the heat exchanger plates with streamlined rib structure of the invention, including substrate and setting are in substrate table
Face is in multiple streamlined ribs of column-row arrangement, and the cross section of streamlined rib is substantially in symmetrical airfoil structure, including leading edge 10, rear
20, upper camber line 31,32 and lower camber line 41,42, the line between aerofoil profile leading edge 10 and rear 20 are formed as wing middle camber line, on
Camber line and lower camber line are symmetrical above and below about middle camber line, and the maximum gauge of aerofoil profile is formed in the maximum inscribed circle position of upper and lower camber line
Place, the center location of maximum inscribed circle is located on middle camber line, the diameter 2R1 of maximum inscribed circle for middle arc length L1 15%~
30%.Aerofoil profile is formed as smooth front end at its leading edge 10.
Upper and lower camber line includes 31,41 and the second section 32,42 of the first section.First section 31,41 is from wing leading edge
10 extend at maximum inscribed circle position, the first section 31,41 be spirogyrate smooth curve, the front end of spirogyrate smooth curve with
Nose radius is tangent, and rear end is tangent with maximum inscribed circle；Second section 32,42 extends to wing rear 20 from maximum inscribed circle
Place, the second section is concave shaped smooth curve, and the front end of concave shaped smooth curve and maximum inscribed circle are tangent.First section
31,41 and the second sections 32,42 form smooth full curve at maximum inscribed circle.
The present invention provides the airfoil structures that two kinds are directed to different flow size.For being suitable for the airfoil structure of small flow
(calling FIN-II in the following text), as shown in Fig. 3 (B), Fig. 4 (B), the distance between the center of circle of maximum inscribed circle and leading edge 10 are middle camber line
The 25%~35% of length L1, such as 29.7%, and the rear end of concave shaped smooth curve 32,42 at rear 20 with middle camber line phase
It cuts, aerofoil profile is formed as wedge angle at rear 20.Concave shaped smooth curve 32,42 is the circle arc curve of indent, circle arc curve
The center of circle and rear point line perpendicular to middle camber line.NACA series of symmetric aerofoil profile employed in compared with the prior art is (such as
Shown in Fig. 3 (A), Fig. 4 (A), call FIN-I in the following text), airfoil structure FIN-II of the invention, by existing aerofoil profile from its widest point it
Lower edge convex outer curve form is changed to the inner concave curve form tangent with maximum inscribed circle and airfoil mean line on tail portion afterwards, relatively
In existing structure form, new construction changes more acutely before and after the maximum width of aerofoil profile, and tangential direction and fin at rear
Middle arc direction is parallel, more preferably fluid can be guided to flow.
For being suitable for the airfoil structure (calling FIN-III in the following text) of big flow, as shown in Fig. 3 (C), Fig. 4 (C), most imperial palace
The distance between the center of circle of the circle of contact and leading edge 10 are 50% or more of middle arc length L1, and aerofoil profile is formed as having at edge 20 behind
There is the smooth fillet of certain radian, the rear end of concave shaped smooth curve 32,42 and rear fillet are tangent.Spirogyrate smooth curve
31,41 be the circle arc curve of evagination, and the line in the center of circle and the maximum inscribed circle center of circle is perpendicular to middle camber line；The smooth song of concave shaped
Line 32,42 is the circle arc curve of indent, and the center of circle of circle arc curve and the line of rear point are perpendicular to middle camber line.Compared to existing
There are NACA series of symmetric aerofoil profile employed in technology (as shown in Fig. 3 (A), Fig. 4 (A)), airfoil structure FIN- of the invention
III moves to right in the maximum inscribed circle center of circle to wing circumferentially intermediate position, thus wing type head show more class is sharp, and by tail
Portion two sides indent string phase contact is changed to the fillet of certain radian by wedge angle, to adapt to engineering reality.
Manufacturing process be proposed with the method for chemical etching or chemical etching one piece of metal plate (include: 316,304,
The materials metal sheet such as 316L, TA1, TC4, thickness are not less than 0.2mm) produce rib type structure shown in Fig. 3, rib on metal plate
Distribution is as shown in Figure 1.The metal plate for processing rib structure is stacked, entirety is finally combined by Diffusion Welding mode,
Last both ends increase end socket and form complete PCHE heat exchanger.After being successful, the lower end surface of rib upper surface and top panel passes through
Diffusion Welding connects together, so that gap section between one piece of heat exchange rib of slab be made to constitute runner.It can be a laminate and pass through heat
Fluid, a laminate, can also be with plurality of plates by a kind of fluid by cold fluid, other plates are by one other fluid, to reach
To the purpose of heat exchange.
Numerical simulation is conducted heat and flowed under length and width the same terms in three types aerofoil profile rib structure, is emulated
As a result as shown in Figure 5.Airfoil passage structure FIN-II proposed by the present invention suitable for small flow, heat transfer factor are greater than existing
Airfoil structure FIN-I, and Pressure drop factor is less than existing airfoil structure.Airfoil passage knot proposed by the present invention suitable for big flow
Structure FIN-III, although heat transfer factor is minimum, Pressure drop factor is also much smaller than other two.Fig. 4 shows proposed by the present invention suitable
No matter airfoil structure FIN-II form for small flow conducts heat and pressure drop aspect all has very greatly relative to existing structure form
Advantage.
Three kinds of aerofoil profile ribs consider that the comprehensive performance comparison of heat transfer and resistance is as shown in Figure 6.It is ginseng with existing aerofoil profile rib FIN-I
Benchmark is examined, evaluation index is the JF factor (JF=(j/jFin-I)/(f/fFin-I)1/3), the meaning of the JF factor is relative to reference base
Quasi- structure increases the incrementss of heat transfer property under the conditions of unit work consumptiom.Fig. 6 shows the existing aerofoil profile rib as reference data,
The JF factor is 1.The JF factor of aerofoil profile rib FIN-II suitable for small flow and the aerofoil profile rib FIN-III suitable for big flow are greater than
1, illustrate two kinds of aerofoil profiles rib structure FIN-II, FIN-III comprehensive performance proposed by the present invention better than existing aerofoil profile rib structure FIN-
I.Fig. 6 also indicates that, with the increase of fluid velocity, the aerofoil profile rib FIN-II comprehensive performance suitable for small flow becomes after reducing before this
In stabilization, the aerofoil profile rib FIN-III comprehensive performance suitable for big flow tends towards stability after increasing before this, final proposed by the present invention
Two kinds of aerofoil profile rib structure comprehensive performances are similar, and the aerofoil profile rib FIN-III comprehensive performance for being suitable for big flow is slightly better than being suitable for
The aerofoil profile rib FIN-II of small flow.It will be appreciated from fig. 6 that under small flow rate, it is proposed that the aerofoil profile rib for being suitable for small flow is made in selection
FIN-II is main rib type；Under the conditions of big flow, it is proposed that select the aerofoil profile rib FIN-III suitable for big flow to make main rib
Type.
Aerofoil profile rib FIN-II suitable for small flow is relative to existing aerofoil profile rib FIN-I, and tail portion is more rapidly restrained, to make
The fluid that head incoming flow separately squeezes is restrained to middle camber line more quickly in tail portion, to form the jet stream to rib.On the one hand increase
The flow-disturbing degree for having added fluid, improves the concertedness between temperature and velocity field；On the other hand, it is thinned the Heat transfer boundary of tail portion
Layer, to achieve the purpose that heat conduction reinforced.
For aerofoil profile FIN-III rib suitable for big flow relative to existing rib type FIN-I, head more class is sharp, comes head
Stream fluid disturbance start it is not strong, so that fluid-pressure drop be made to greatly reduce.But the design of tail portion fast convergence, makes by by force
It separates and the biggish fluid of pressure flows to rapidly line of symmetry, so that increasing disturbance improves the collaboration of temperature and VELOCITY DISTRIBUTION
Property, heat conduction reinforced purpose.And relative to existing rib type FIN-I, two kinds of aerofoil profile rib structures FIN-II proposed by the present invention,
FIN-III increased fluid passage section product, to reduce the relative pressure drop of flow process；And flow-disturbing degree is also increased
Add, to make heat transfer be strengthened, to keep two kinds of airfoil structures FIN-II, FIN-III heat transfer flow proposed by the present invention comprehensive
Performance is closed to greatly increase relative to existing structure.Of the invention is proposed for efficiency compact high printed circuit board heat exchanger synthesis
The improvement of performance has important and theory significance and practical application value.
The foregoing is merely illustrative of the preferred embodiments of the present invention, is not intended to limit the invention, all in essence of the invention
Within mind and principle, any modification, equivalent substitution, improvement and etc. done be should be included within the scope of the present invention.
Claims (11)
1. including substrate and the substrate surface is arranged in column-row arrangement in a kind of heat exchanger plates with streamlined rib structure
Multiple streamlined ribs, the cross section of the streamlined rib are in symmetrical airfoil structure, including leading edge, rear, upper camber line and lower camber line,
Line between aerofoil profile leading edge and rear is formed as the middle camber line of the aerofoil profile, the upper camber line and lower camber line about in described
Camber line is symmetrical above and below, and the maximum gauge of the aerofoil profile is formed at the maximum inscribed circle position of the upper camber line, lower camber line, described
The center location of maximum inscribed circle is located on the middle camber line, which is characterized in that
The upper camber line, lower camber line include the first section and the second section, wherein
First section extends to from maximum inscribed circle position from the wing leading edge, and first section is spirogyrate light
Sliding curve, the rear end of the spirogyrate smooth curve and the maximum inscribed circle are tangent,
Second section is extended to from the maximum inscribed circle from wing rear, and second section is the smooth song of concave shaped
Line, and the front end of the concave shaped smooth curve and the maximum inscribed circle are tangent,
And
First section and the second section form smooth full curve at the maximum inscribed circle,
First section is set as spirogyrate smooth curve, and the second section is set as concave shaped smooth curve, so that heat exchange stream
Body changes more acutely when flowing through each streamlined rib before and after the maximum width of streamlined rib, so that it is logical to improve aerofoil profile
The heat exchange property in road.
2. heat exchanger plates according to claim 1, which is characterized in that the diameter of the maximum inscribed circle is that the middle camber line is long
The 15%~30% of degree.
3. heat exchanger plates according to claim 1, which is characterized in that the aerofoil profile is formed as smooth front end in its edge.
4. heat exchanger plates according to claim 3, which is characterized in that the front end of the spirogyrate smooth curve and nose radius
It is tangent.
5. heat exchanger plates according to claim 1, which is characterized in that between the center of circle and leading edge of the maximum inscribed circle away from
From 25%~35% for the middle arc length, and the rear end of the concave shaped smooth curve at the rear with it is described in
Tangential, the aerofoil profile are formed as wedge angle at rear.
6. heat exchanger plates according to claim 5, which is characterized in that the concave shaped smooth curve is the arc-shaped song of indent
Line, the center of circle of the circle arc curve and the line of rear point are perpendicular to the middle camber line.
7. heat exchanger plates according to claim 1, which is characterized in that between the center of circle and leading edge of the maximum inscribed circle away from
From 50% or more for the middle arc length, the aerofoil profile is formed to have the smooth fillet of certain radian at edge behind,
The rear end of the concave shaped smooth curve and the smooth fillet of the rear are tangent.
8. heat exchanger plates according to claim 7, which is characterized in that the spirogyrate smooth curve is the arc-shaped song of evagination
The line in line, the center of circle and the maximum inscribed circle center of circle is perpendicular to the middle camber line；The concave shaped smooth curve is indent
Circle arc curve, the center of circle of the circle arc curve and the line of rear point are perpendicular to the middle camber line.
9. heat exchanger plates according to claim 1, which is characterized in that the streamlined rib uses chemical etching, laser-induced thermal etching
Or mach mode is formed on the substrate.
10. heat exchanger plates according to claim 1, which is characterized in that the substrate is the metal that thickness is not less than 0.2mm
Plate.
11. a kind of printed circuit sheet heat exchanger, including several the claims 1 to 10 are described in any item with streamlined
The heat exchanger plates of rib structure, wherein the heat exchanger plates with streamlined rib structure mutually stack, and by way of Diffusion Welding
Be formed as whole.
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| CN201710663123.7A CN107687780B (en) | 2017-08-05 | 2017-08-05 | Heat exchanger plates with streamlined rib structure and the printed circuit sheet heat exchanger comprising it |
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| CN201710663123.7A CN107687780B (en) | 2017-08-05 | 2017-08-05 | Heat exchanger plates with streamlined rib structure and the printed circuit sheet heat exchanger comprising it |
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| CN107687780B true CN107687780B (en) | 2019-06-18 |
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| CN115014107B (en) * | 2022-05-26 | 2023-04-07 | 西安交通大学 | Double-effect enhanced heat exchange micro-channel heat sink with airfoil flow distribution ribs |
| CN115638654B (en) * | 2022-11-15 | 2023-03-17 | 沈阳鑫博工业技术股份有限公司 | Spodumene mineral powder phase change conversion device |
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| CN107687780A (en) | 2018-02-13 |
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Inventor after: Guo Jiangfeng Inventor after: Cui Xinying Inventor after: Huai Xiulan Inventor after: Cheng Keyong Inventor after: Xiang Mengru Inventor before: Guo Jiangfeng Inventor before: Cui Xianying Inventor before: Huai Xiulan Inventor before: Cheng Keyong Inventor before: Xiang Mengru |